CanSat Interim Presentation II Samuel Rustan (EE) Yasmin Belhaj (ME) Andrew Guerr (CE) Andrew Grant (ME) Maxwell Sandler (ME) Technical Advisors: Dr. David Cartes, Dr. Victor DeBrunner Course Instructors: Dr. Kamal Amin, Dr. Michael Frank ME Senior Design Team #18 ECE Senior Design Team #10 March 19, 2013

Overview Mission Recap Finalized design and configurations Fabrication Update Electronics and Integration Software development Timeline and Budget Tasks remaining Presenter: Samuel Rustan

CanSat Project Overview Design a container/payload system to be launched via rocket and develop autonomous descent control strategy to safely land CanSat Container will house payload for initial descent Payload will house electronic components and “sensor” (egg) Telemetry data will be transmitted for flight duration Sample Design Parameters and Restrictions Size Mass Material Descent Control Strategy Presenter: Samuel Rustan

CanSat Project Overview Sequence of action Rocket supplied by AIAA, with specified rocket bay dimensions Phase 1 from rocket detachment to 400 m: Per guidelines, a parachute or streamer must be used to decrease velocity to 20 m/s by 400 m mark. Phase 2 from 400 m to ground level: Payload must detach from container. An aero-braking device (non-parachute) must deploy at 400 m to safely land Payload. The initial parachute will continue to control descent of container. Telemetry data transmitted includes GPS data, altitude, air temperature, battery voltage, and flight software state. Force sensor will be used to calculate force of impact from Payload. Presenter: Samuel Rustan

Previous Benchmarks Finalized design for launch and descent Compared passive braking method Parachute vs. Streamer Determined egg protection strategy Iterative trials, various materials Selectable Objective – Impact Force Sensor Procured and tested electronic components Delivered successful Preliminary Design Review (PDR) Feedback: Scored 92% from AIAA/NASA Panel Presenter: Samuel Rustan

Updated Launch Configuration Container Payload Egg Compartment Electronic Components Shelving Separation Mechanism Parachute Aero-braking Structure Explain selection of each subsystem: Container is the entire length of structure. Made of plastic, it is open on the bottom. Payload is the portion inside that houses the electronic components and the raw egg. Parachute was selected by conducting an experiment on the braking efficacy and ease of implementation of parachutes and streamers for this application. The diameter of the parachute was calculated to achieve the desired 20 m/s at 400m. While under descent of parachute, the payload will detach from the container via this separation mechanism. A motor will provide the rotation of this ring to allow the payload to fall from out from the bottom. The aero-braking structure is secured in its launch configuration, surrounding the payload. Support rods connect the top and bottom portions of the aero-braking structure to the payload. Electronic components are in the top portion of the payload, and the egg is housed near the bottom.

Updated Descent Configuration -Maintained idea to use ABS Plastic and 3-D print top and bottom of aero-braking structure, on top of which we can mount the motor that controls the separation mechanism -Torsional springs will be used to deploy these rods which have fabric attached in between -These springs are held in compression by a wire running through the bottom, and released when a heating element breaks the wire slightly below 400m -New components include a wire running from the bottom of the aero-braking structure to the ends of the rod, to secure the angle during deployment Torsion Spring Torque of 2.14 [in*lb]

Fabrication Update Parts have been procured and machined -Still waiting on parachute -Dimensions have not been changed since last presentation -Allow clearance in the rocket section of 130 mm x 250 mm -Overcome sizing issues of micro-controller, motor, and payload -Challenge meeting 700g weight requirements. Solution– use alternative egg protection method and/or alter material of support rods (aluminum, wood, plastic) Parts have been procured and machined Dimensions finalized to fit in rocket bay Mass budget concerns (underweight)

Fabrication Update Top Left: Side View with Aerobrake deployed Top Right: Aerobrak cut-away with antenna Bottom Left: Top View with aero-brake deployed Presenter: Andrew Grant

Release Mechanism Prototype Presenter: Andrew Grant

Sensor (Egg) Protection Polystyrene beads chosen from experiment 1050 [kg/m3] -Polystyrene beads chosen to protect egg -Will be inserted in the bottom portion of the CanSat as seen in above image Presenter: Andrew Grant

Integration of Electrical Components Each sensor on separate circuit board #2 & #1 screws used to attach to plastic platforms Glue to secure Rubber footpads used to separate components from platform Holes will be drilled in platform to provide wire bundle channel (not shown) -Multi-Level Electronics Arrangement -Permanently Affixed to Payload Half -Rigid shelves made of plastic Presenter: Samuel Rustan

Configuration of Telemetry Components CanSat Onboard Electronics To Antenna USB XBEE Antenna Ground Station -Multi-Level Electronics Arrangement -Permanently Affixed to Payload Half -Rigid shelves made of plastic Note: USB cables for programming only Presenter: Samuel Rustan

Integration of Electrical Components Accelerometer Press/Temp GPS Module Microcontroller -Multi-Level Electronics Arrangement -Permanently Affixed to Payload Half -Rigid shelves made of plastic Battery XBEE Radio Presenter: Samuel Rustan

Communications: Range Tests Packet Loss: 0% 10% 30% 50% Lost Ground Level Distance [m] Test 1-6: 45 65 80 110 115+ ~3 [m] high Tests 7-10 60 120 140 180 190+ Results 2.4 GHz, 60 mW Insufficient Range Improper Test Link Margin: 20 [dB] Receiver Sensitivity: 100 [dB] Received Power: 80 [dB] Link Margin = 100 – 80 Enough margin to maintain link (accord. To Digi RF Tech) Proposed Solutions Increase Gain of Receiver Ant Digi Int’l RF Engineer Proper range test (5 [m] above any obstacle) Presenter: Samuel Rustan

Ground Control Software Flight Software Working “Beta” version Migration is “so far good” No noticeable difference between the Uno and Mini functionality Ground Station Software Version 5, working “alpha” version Written in Python Both Mac (shown) & PC versions Not yet fully integrated with all subsystems Presenter: Andrew Guerr

Flight Software Current Working “Beta” version Transmits telemetry data packet Integrated with altimeter and GPS Errors reading GPS data Needs Integration with accelerometer, voltage divider, buzzer, and motor Support for user entry of altitude correction data Altitude smoothing Presenter: Andrew Guerr

Updated Gantt

Total Procurement Expenditures Funding / Project Budget Revenue Expenses Funding Source Funds Received Procured Expense Amount ECE Department $200.00 ECE Components (Telemetry) 300 Private Donation $750.00 Mechanical & Structural 70 Dr. Shih $1000.00 Shipping 15.00 State Farm $250.00 Total Funds Generated $2200.00 Total Procurement Expenditures 385 Total Available Funds Remaining $1815.00

Looking Forward Parachute attachment Complete fabrication of CanSat Emphasis on Open House Display Test separation mechanism and aero-braking deployment using altimeter Complete microcontroller migration Complete range testing Demonstrate Telemetry with FSW & GCSW Prepare User Manual Present AIAA Critical Design Review (Mar 29th) Prepare Open House Demonstration (April 18th)